A multilayered thick cylindrical shell under internal pressure and thermalloads applicable to solid propellant rocket motors

A solid propellant rocket motor can be considered to be made of various cir cumferential layers of different properties. A simple procedure is describe d here to obtain an analytical solution for the general case of multilayere d thick cyclindrical shell. for internal pressure and thermal loads. This a nalytical procedure is useful in the preliminary design analysis of solid p ropellant rocket motors. Since solid propellant material is of viscoelastic behaviour an approximate viscoelastic solution methodology for the multila yered shell is described for estimation of time dependent solutions of prop ellant grain in a rocket motor. The analytical solution for a two layer rei nforced thick cylindrical shell available in the literature is shown to be a special case of the present analytical solution. The results from the pre sent analytical solution for multilayers is found to be in good agreement w ith FEA results.